Gas turbine combustor, and gas turbine with the combustor

ABSTRACT

In order to realize a stable decrease in NOx, a gas turbine combustor is supplied which can reduce combustion vibration. A combustor ( 3 ) is provided with a first box body ( 30 ), which is installed outside an object body ( 20 ) such as a combustor basket ( 6 ), a transition piece ( 7 ) or a bypass duct ( 11 ) so as to form a first internal space ( 31 ) having a predetermined capacity; and a first throat ( 32 ) having a predetermined length which has one end ( 32   a ) open to a side wall ( 20   a ) of the object body ( 20 ) and has the other end ( 32   b ) open to a first internal space ( 31 ); wherein, a first resistive element ( 33 ) having a multiple number of through-holes is inserted and engaged to one end ( 32   a ). Fluid particles serving as vibration elements of combustion vibration caused in a combustion region are effectively trapped by the first resistive element ( 33 ) and at the same time resonate with the air of the first internal space ( 31 ) being connected through the first throat ( 32 ) and vibrate in the neighborhood of the first resistive element ( 33 ), thereby damping vibration amplitude thereof.

TECHNICAL FIELD

The present invention relates to a gas turbine combustor (sometimesreferred as a “combustor” hereinafter) and a gas turbine equipped with agas turbine combustor, and especially, relates to a gas turbinecombustor and a gas turbine that reduce combustion vibration in order torealize decrease in nitrogen oxides (NOx).

BACKGROUND ART

Conventionally, a gas turbine has an air compressor (sometimes referredas a “compressor” hereinafter), a combustor and a turbine serve as majorcomponents, wherein the combustor is installed between the compressorand the turbine that are directly connected to each other by a mainshaft; an air serving as a working fluid is inhaled into the compressorby rotation of the main shaft and compressed therein; the compressed airis introduced into the combustor and burned with a fuel; and the hightemperature and high pressure combustion gas is exhausted into a turbineso as to rotary-drive the main shaft with the turbine. The gas turbineconstructed in such a manner is utilized as a driving source by having agenerator and the like connected to the front end of the main shaft, andis also utilized as a jet engine by installing an exhaust port forinjection of combustion gas at the front of the turbine.

And now, in recent years, especially reduction of NOx in exhaust gasbeing discharged from a gas turbine is strongly desired for anenvironmental issue as one of vital legal regulations. Therefore, acombustor which actually generates NOx especially requires a technologyto suppress generation of NOx. In order to achieve this, as a combustionmethod to be adopted to a combustor, a premixed combustion method hasbecome a main stream, wherein a fuel and compressed air are burned afterbeing mixed preliminarily. In this premixed combustion method, because afuel disperses uniformly and tenuously in the compressed air, localincrease in temperature of combustion flame can be prevented, therebymaking it possible to reduce the generation amount of NOx whichincreases in accordance with an increase in temperature of combustionflame.

Here, a more common gas turbine than conventional to which a combustorusing a premixed combustion method is applied will be described byreferring to FIG. 47. This gas turbine 1 mainly consists of a compressor2, a gas turbine combustor 3 and a turbine 4. The combustor 3 isinstalled to a casing 5 which has a cavity being formed between thecompressor 2 and the turbine 4, and consists of a combustor basket 6which has a combustion region; a transition piece 7 which is connectedto the front end of the combustor basket 6: an outer shell 8 which isinstalled so as to be concentric to the combustor basket 6; a pilotnozzle 9 which is installed on the axis of the combustor basket 6 fromthe rear end; a plurality of main nozzles 10 which are installed at evenintervals in a circumferential direction around the pilot nozzle 9; abypass duct 11 which opens to the casing 5 being connected to a sidewall of the transition piece 7; a bypass valve 12 which is installed tothe bypass duct 11; and a bypass-valve variable mechanism 13 whichadjusts the degree of opening and closure of the bypass valve 12. (Seethe Japanese Patent Application Laid-Open No. 2001-254634, for example.)

Being constructed as mentioned above, compressed air being compressed inthe compressor 2 flows into the casing 5 (an outline arrow in thedrawing), reverses for approximately 180 degrees (arrows in solid linein the drawing) after going through a tubular space which is formed byan outer circumference surface of the combustor basket 6 and an innercircumference surface of an outer shell 8, and is introduced into thecombustor basket 6 from the rear-end side. Next, a fuel is blasted tothe pilot burner (not illustrated) at the front end of the pilot nozzle9 and be subject to diffusion combustion and is also subject to premixedcombustion by being mixed with a fuel injected to the main burner (notillustrated) at the front end of each of the main nozzles 10, so as tobecome high temperature and high pressure combustion gas. The combustiongas goes through the internal of the transition piece 7 and is exhaustedfrom the front end thereof, so as to drive the turbine 4. In addition, apart of compressed air (sometimes referred as “bypass air” hereinafter)inside the casing 5 is supplied to the internal of the transition piece7 from the bypass duct 11, which plays a role of adjusting the densityof combustion gas.

However, although the above-mentioned pre-mixed combustion methodseemingly excels in reduction of NOx, it has a problem that combustionvibration is easy to occur because flame is thin and burns in a narrowregion in a short time, resulting in an excessive combustion energy perunit space. This combustion vibration is generated by having a part ofcombustion energy converted into vibrational energy, and not onlyproduces significant vibration and noise when it propagates as apressure wave and resonates with an acoustical system consisting ofcasings of a combustor, a gas turbine and the like but also inducespressure fluctuation and heat-generation fluctuation inside thecombustor, thereby making state of combustion unstable, which eventuallyinterferes a decrease in NOx.

In order to cope with such a problem of combustion vibration asmentioned above, conventionally, by actually operating a gas turbine,appropriate adjustment is made so as to operate it in a normal conditionand, at the same time, regular operational conditions are set as needed.Therefore, cumbersome adjustment activities are indispensable.

Additionally, a conventional combustor trying to reduce the combustionvibration has a resonator having a cavity installed around the outercircumference of a combustor basket and a transition piece which serveas cylinder bodies having a combustion region therein, and hassound-absorption holes opening to the cavity formed therein. (See FIG. 1through FIG. 3 on pages 3 through 5 of the Japanese Patent ApplicationLaid Open No. 2002-174427, for example.) By this combustor, fluidparticles serving as vibration elements of the combustion vibration thatoccurs in the combustion region resonate with the air in the cavityinside the resonator and vibrate through the sound-absorption holes,damping the vibration amplitude thereof. In this way, it is possible toreduce the combustion vibration, thereby realizing more or less adecrease in NOx.

However, in the conventional combustor trying to reduce the combustionvibration as mentioned above, it is originally assumed that thecombustion vibration occurs in a high-frequency area. Therefore, it iseffective to the combustion vibration in a high-frequency area, but atthe same time, it cannot be said to thoroughly cope with the combustionvibration in a low-frequency area.

DISCLOSURE OF THE INVENTION

It is an object of the present invention to provide a gas turbinecombustor and a gas turbine that can reduce the combustion vibration inorder to realize a decrease in NOx in a stable manner. Furthermore, itis another object to provide a gas turbine combustor and a gas turbinethat can reduce the combustion vibration, irrespective of the frequencyareas.

In order to achieve the above-mentioned object, a gas turbine combustoraccording to the present invention, comprising a cylinder body which hasa combustion region therein, is provided with a first box body which isinstalled outside the cylinder body, forming a first internal spacehaving a predetermined capacity; and a first throat having apredetermined length which has one end thereof open to the combustionregion or a downstream area thereof and has the other end thereof opento the first internal space; and has a first resistive element having amultiple number of through-holes inserted and engaged into the one endof the first throat. By this, fluid particles serving as vibrationelements of the combustion vibration that occurs in the combustionregion are effectively trapped by the first resistive element; resonatewith the air in the first internal space being connected through thefirst throat; and vibrate in the neighborhood of the first resistiveelement, damping the vibration amplitude thereof. In this way, it ispossible to reduce the combustion vibration and realize a stabledecrease in NOx. Here, the object to which one end of the first throatopens is a combustor basket or a transition piece which makes up thecylinder body or a bypass duct which is connected to a side wall of thecylinder body.

Additionally, in order to achieve the above-mentioned object, accordingto the present invention, a gas turbine combustor, comprising a cylinderbody which has a combustion region therein, is provided with a box bodywhich is installed outside the cylinder body, forming an internal spacehaving a predetermined capacity; and a throat having a predeterminedlength which has one end thereof open to an area upstream of thecombustion region and has the other end thereof open to the internalspace; and has a resistive element having a multiple number ofthrough-holes inserted and engaged into the one end of the throat. Bythis, fluid particles serving as vibration elements of the combustionvibration that occurs in a combustion region are effectively trapped bythe resistive element; resonate with the air in the internal space ofthe box body being connected through the throat; and vibrate in theneighborhood of the resistive element, damping the vibration amplitudethereof. In this way, it is possible to reduce the combustion vibrationand realize a stable decrease in NOx. Here, the object to which one endof the throat opens is a combustor basket which makes up the cylinderbody or an outer shell which is installed so as to be concentric withthe combustor basket.

In addition, in order to achieve the above-mentioned object, accordingto the present invention, a gas turbine is equipped with an aircompressor and a turbine being directly connected to each other by amain shaft and a plurality of gas turbine combustors being installed onthe same circumference of the main shaft between the air compressor andthe turbine and consisting of a cylinder body each of which has acombustion region therein; wherein, are provided a first annulus pipebody which is installed outside the rear end of each of the cylinderbodies concentrically with the main shaft and a first throat having apredetermined length which has each of one ends open to an area upstreamof each of the combustion regions and has each of the other ends open tothe inside of the first annulus pipe body; and wherein, a firstresistive element having a multiple number of through-holes is insertedand engaged into each of the one ends of each of the first throats. Bythis, fluid particles are effectively trapped by each of the firstresistive element; resonate with the air inside the first annulus pipebody being connected through each of the first throats; and vibrate inthe neighborhood of each of the first resistive elements, damping thevibration amplitude thereof. In this way, it is possible to reduce thecombustion vibration and eventually realize a stable decrease in NOx asan entire gas turbine, thereby achieving a reduction of NOx in exhaustgas. Here, the object to which each of the ends of each of the firstthroats opens is each of combustor baskets which makes up each of thecylinder bodies or each of outer shells which is installedconcentrically with each of the combustor baskets.

Furthermore, in order to achieve the above-mentioned object, accordingto the present invention, a gas turbine combustor, comprising a cylinderbody which has a combustion region therein and a bypass duct which hasone end open to the combustion region or a downstream area thereof inthe cylinder body and has the other end open to the internal of a casingforming the periphery of the cylinder body; wherein, is installed aplate-type member which has a multiple number of through-holes andcrosses the bypass duct. By this, fluid particles serving as vibrationelements of the combustion vibration that occurs in a combustion regionare introduced from one end of the bypass duct and effectively trappedin each of the through-holes of the plate-type member; resonate with theair inside the casing being connected through the bypass duct; andvibrate through each of the through-holes, damping the vibrationamplitude thereof. In this way, it is possible to reduce the combustionvibration and realize a stable decrease in NOx.

Moreover, in order to achieve the above-mentioned object, according tothe present invention, a gas turbine combustor, comprising a cylinderbody which has a combustion region therein and a bypass duct which hasone end open to the combustion region or a downstream area thereof inthe cylinder body and has the other end open to the internal of a casingforming the periphery of the cylinder body; wherein, are provided adividing wall which crosses in the neighborhood of the one end of thebypass duct, a protruding pipe which goes through this dividing wall andprotrudes from at least one surface of the dividing wall, and aresistive element which is inserted and engaged into this protrudingpipe and has a multiple number of through-holes. By this, fluidparticles are effectively trapped by the resistive element; resonatewith the air in a space from the dividing wall inside the bypass ductbeing connected through the protruding pipe to the other end; andvibrate in the neighborhood of the resistive element, damping thevibration amplitude thereof. In this way, it is possible to reduce thecombustion vibration and realize a stable decrease in NOx.

Furthermore, in order to achieve the above-mentioned object, accordingto the present invention, a gas turbine is equipped with an aircompressor, any of the above-mentioned gas turbines and a turbine.Therefore, it is possible to reduce the combustion vibration in a gasturbine combustor and realize a stable decrease in NOx, therebyachieving a reduction of NOx in exhaust gas.

And, in order to achieve the above-mentioned object further, accordingto the present invention, a gas turbine combustor, comprising a cylinderbody having a combustion region therein; wherein, the cylinder body hasa resonator having a cavity installed around the outer circumferencethereof; has sound-absorption holes opening to the cavity formedtherein; and is provided with a first box body which is installed so asto be adjacent to the resonator, forming a first internal space having apredetermined capacity, and a first throat which has one end thereofopen to the cavity and has the other end thereof open to the firstinternal space. By this, fluid particles serving as vibration elementsin a high-frequency area of the combustion vibration that occurs in acombustion region resonate with the air in a cavity inside the resonatorand vibrate through the sound-absorption holes, damping the vibrationamplitude thereof. On the other hand, fluid particles serving asvibration elements in a low-frequency area resonate with the air in afirst internal space being connected through a first throat through thecavity inside the resonator and vibrate through the sound-absorptionholes, damping the vibration amplitude thereof. In this way, it ispossible to reduce the combustion vibration, regardless of frequencyareas, and realize a stable decrease in NOx.

Then, in order to achieve the above-mentioned object further, accordingto the present invention, a gas turbine is provided with an aircompressor, the above-mentioned gas turbine combustor and a turbine.Therefore, it is possible to reduce the combustion vibration in a gasturbine combustor, regardless of frequency areas, and realize a stabledecrease in NOx, thereby achieving a reduction of NOx in exhaust gas.

BRIEF DESCRIPTION OF THE DRAWINGS

FIG. 1 is a cross section showing a concept of a combustor in accordancewith a first embodiment of the prevent invention.

FIG. 2 is a cross section showing a concept of a combustor in accordancewith a second embodiment of the prevent invention.

FIG. 3 is a cross section showing a concept of a combustor in accordancewith a third embodiment of the prevent invention.

FIG. 4 is a cross section showing a concept of a combustor in accordancewith a fourth embodiment of the prevent invention.

FIG. 5 is a cross section showing a concept of a combustor in accordancewith a fifth embodiment of the prevent invention.

FIG. 6 is a cross section showing a concept of a combustor in accordancewith a sixth embodiment of the prevent invention.

FIG. 7 is a cross section showing a concept of a combustor in accordancewith a seventh embodiment of the prevent invention.

FIG. 8 is a cross section showing a concept of a combustor in accordancewith an eighth embodiment of the prevent invention.

FIG. 9 is a longitudinal cross-sectional view of a necessary portionshowing one example of a gas turbine to which a combustor in accordancewith a first through eighth embodiments of the present invention isapplied concretely.

FIG. 10 is a transverse cross-sectional view corresponding to the crosssection A-A of FIG. 9.

FIG. 11 is a transverse cross-sectional view corresponding to the crosssection A-A in FIG. 9, showing another example of a gas turbine to whicha combustor in accordance with a first through eighth embodiments of thepresent invention is applied concretely.

FIG. 12 is an exemplary longitudinal cross-sectional view of a necessaryportion showing a neighborhood of a gas turbine combustor in accordancewith a ninth embodiment of the present invention.

FIG. 13 is an exemplary longitudinal cross-sectional view of a necessaryportion showing a neighborhood of a gas turbine combustor in accordancewith a tenth embodiment of the present invention.

FIG. 14 is an exemplary longitudinal cross-sectional view of a necessaryportion showing a neighborhood of a gas turbine combustor in accordancewith an eleventh embodiment of the present invention.

FIG. 15 is an exemplary longitudinal cross-sectional view of a necessaryportion showing a neighborhood of a gas turbine combustor in accordancewith a twelfth embodiment of the present invention.

FIG. 16 is an exemplary transverse cross-sectional view of a necessaryportion showing a neighborhood of a gas turbine combustor in accordancewith a twelfth embodiment of the present invention.

FIG. 17 is an exemplary transverse cross-sectional view of a necessaryportion showing a neighborhood of a gas turbine combustor in accordancewith a thirteenth embodiment of the present invention.

FIG. 18 is an exemplary longitudinal cross-sectional view of a necessaryportion showing a neighborhood of a gas turbine combustor in accordancewith a fourteenth embodiment of the present invention.

FIG. 19 is a longitudinal cross-sectional view of a necessary portion ofa combustor in accordance with a fifteenth embodiment of the presentinvention.

FIG. 20 is a transverse cross-sectional view of a necessary portion of acombustor in accordance with a fifteenth embodiment.

FIG. 21 is a longitudinal cross-sectional view of a necessary portion ofa combustor in accordance with a sixteenth embodiment of the presentinvention.

FIG. 22 is a plan view of a plate-type member of a combustor inaccordance with a sixteenth embodiment.

FIG. 23 is a plan view of a bypass valve of a combustor in accordancewith a sixteenth embodiment.

FIG. 24A and FIG. 24B are longitudinal cross-sectional views of anecessary portion showing a behavior to adjust the bypass air amount ina combustor in accordance with a sixteenth embodiment.

FIG. 25A and FIG. 25B are longitudinal cross-sectional views of anecessary portion showing a behavior to reduce damping vibration in acombustor in accordance with a sixteenth embodiment.

FIG. 26 is a longitudinal cross-sectional view of a necessary portion ofa combustor in accordance with a seventeenth embodiment of the presentinvention.

FIG. 27 is a plan view of a plate-type member in a combustor of aseventeenth embodiment.

FIG. 28 is a longitudinal cross-sectional view of a necessary portion ofa combustor in accordance with an eighteenth embodiment of the presentinvention.

FIG. 29 is a longitudinal cross-sectional view of a necessary portion ofa combustor in accordance with a nineteenth embodiment of the presentinvention.

FIG. 30 is a longitudinal cross-sectional view of a necessary portion ofa combustor in accordance with a twentieth embodiment of the presentinvention.

FIG. 31 is a longitudinal cross-sectional view of a necessary portionshowing one example of a combustor in accordance with a twenty-firstembodiment of the present invention.

FIG. 32 is a longitudinal cross-sectional view of a necessary portion ofa combustor in accordance with a twenty-second embodiment of the presentinvention.

FIG. 33 is a projected cross-sectional view of a resonator and a firstbox body in a combustor in accordance with a twenty-second embodimentthat are cut circumferentially and developed.

FIG. 34 is a longitudinal cross-sectional view of a necessary portion ofa combustor in accordance with a twenty-third embodiment of the presentinvention.

FIG. 35 is a projected cross-sectional view of a resonator and a firstbox body in a combustor in accordance with a twenty-third embodimentthat are cut circumferentially and developed.

FIG. 36 is a longitudinal cross-sectional view of a necessary portion ofa combustor in accordance with a twenty-fourth embodiment of the presentinvention.

FIG. 37 is a projected cross-sectional view of a resonator and a firstbox body in a combustor in accordance with a twenty-fourth embodimentthat are cut circumferentialy and developed.

FIG. 38 is a longitudinal cross-sectional view of a necessary portion ofa combustor in accordance with a twenty-fifth embodiment of the presentinvention.

FIG. 39 is a projected cross-sectional view of a resonator and a firstbox body in a combustor in accordance with a twenty-fifth embodimentthat are cut circumferentially and developed.

FIG. 40 is a projected cross-sectional view of a resonator and a firstbox body in a combustor in accordance with a twenty-sixth embodiment ofthe present invention that are cut circumferentially and developed.

FIG. 41 is a projected cross-sectional view of a resonator and a firstbox body in a combustor in accordance with a twenty-seventh embodimentof the present invention that are cut circumferentially and developed.

FIG. 42 is a projected cross-sectional view of a resonator and a firstbox body in a combustor in accordance with a twenty-eighth embodiment ofthe present invention that are cut circumferentially and developed.

FIG. 43 is a projected cross-sectional view of a resonator and a firstbox body in a combustor in accordance with a twenty-ninth embodiment ofthe present invention that are cut circumferentially and developed.

FIG. 44 is a longitudinal cross-sectional view of a necessary portion ofa combustor in accordance with a thirtieth embodiment of the presentinvention.

FIG. 45 is a longitudinal cross-sectional view of a necessary portion ofa combustor in accordance with a thirty-first embodiment of the presentinvention.

FIG. 46 is a projected cross-sectional view of a resonator and a firstbox body in a combustor in accordance with a thirty-first embodimentthat are cut circumferentially and developed.

FIG. 47 is a longitudinal cross-sectional view of a necessary portion inthe neighborhood of a combustor of a general gas turbine.

BEST MODE FOR CARRYING OUT OF THE INVENTION

Referring now to the drawings, embodiments of the present invention willbe described hereinafter. First a first through eighth embodiments ofthe present invention will be explained in sequence. FIG. 1 is across-sectional view showing a concept of a combustor in accordance witha first embodiment of the present invention. In the drawings, samesymbols will be supplied to portions which have same name and samefunction as in FIG. 47 and the overlapping explanations will be omitted.The same will apply to a second through eighth embodiments of thepresent invention to be hereinafter described.

A combustor 3 in accordance with a first embodiment of the presentinvention is applied to a gas turbine 1 shown in FIG. 47. As shown inFIG. 1, a first box body 30 is installed outside a side wall 20 a of anobject body 20, and a first internal space 31 having a predeterminedcapacity is formed by a cavity inside the first box body 30.Additionally, the first box body 30 is connected to the side wall 20 athrough a first tubular throat 32 having a predetermined length, and thefirst throat 32 has one end 32 a open to the internal of the object body20 from the side wall 20 a and has the other end 32 b open to the firstinternal space 31.

Further, a first resistive element 33 having a multiple number ofthrough-holes is inserted and engaged into one end 32 a of the firstthroat 32. The first resistive element 33 is, for example, a punchingmetal, a ceramic sintered metal or a sintered metallic mesh. Inaddition, the object body 20 mentioned herein is a cylinder body such asthe combustor basket 6 having a combustion region therein or thetransition piece 7 in an area downstream thereof, or the bypass duct 11being connected to the side walls thereof and is an object whose insidehas combustion vibration propagate.

Constructed as described above, the first box body 30 functions as anair-container body which accommodates the air for resonance for fluidparticles serving as vibration elements of the combustion vibration thatoccurs in a combustion region inside the combustor basket 6.Additionally, the first throat 32 functions as a junction body whichconnects the object body 20 and the first box body 30. Moreover, thefirst resistive element 33 functions as a transverse body which crossesinside the first throat 32, and through-holes thereof function as ventswhere fluid particles are vibrated by resonance with the air inside thefirst box body 30. In this way, as for the combustion vibration thatoccurs in a combustion region inside the combustor basket 6, fluidparticles serving as vibration elements thereof are effectively trappedby the first resistive element 33 by propagating inside the object body20; and then resonate with the air in a first internal space 31 beingconnected through the first throat 32 and vibrate in the neighborhood ofthe first resistive element 33. By this vibration, vibration amplitudeof the fluid particles is damped and the combustion vibration thereof isreduced. As a result, a stable reduction of NOx is realized.

Additionally, in FIG. 1, one first throat 32 is installed for the firstbox body 30. However, needless to say, more than two first throats 32may be installed.

Then, a second embodiment of the present invention will be described byreferring to FIG. 2. Characteristic of a second embodiment is thatconsideration is given especially to combustion vibration in alow-frequency area in a first embodiment. When combustion vibrationoccurs in a low-frequency area, it is necessary to make across-sectional area inside the first throat 32 in accordance with thefirst embodiment smaller. However, if doing so, an area where the firstresistive element 33 exists inevitably becomes smaller, which reducesthe ratio of fluid particles to be trapped, contributing to a decreasein combustion vibration insufficiently as a whole.

Consequently, in accordance with this embodiment, such a stepped tubularobject is applied as the first throat 32 as an inner circumferencethereof is rapidly spread from one end 32 b to the other end 32 a in theneighborhood of the center, wherein an opening area of one end 32 athereof is larger than that of the other end 32 b. The first resistiveelement 33 is inserted and engaged into one end 32 a.

Because in this way, it is possible to make an internal of the firstthroat 32, namely the cross-sectional area of the other end 32 b,smaller and at the same time, expand a region where the first resistiveelement 33 exists, the ratio of trapping of fluid particles in alow-frequency area is increased, thereby contributing to a reduction ofcombustion vibration sufficiently as a whole. As a result, it ispossible to reduce thoroughly the combustion vibration in alow-frequency area as a whole.

Additionally, when a trumpet-like object whose inner circumferencegradually expands is applied as the first throat 32, the same effectscan be obtained.

Next, a third embodiment of the present invention will be described byreferring to FIG. 3. Characteristic of a third embodiment is thatconsideration is given to adverse effects that occur in the secondembodiment. As the second embodiment, when an opening area of one end 32a is larger than that of the other end 32 b in the first throat 32,namely when the capacity inside the first throat 32 becomes larger,sometimes a phase difference does not occur for each of pressurefluctuations between a space inside the first throat 32 being isolatedby the first resistive element 33 and a space of the object body 20 (“+”and “+” in the drawing). In such a case, because fluid particles do notvibrate in the neighborhood of the first resistive element 33, such anadverse effect is caused as combustion vibration in a low-frequency areacannot be reduced sufficiently if nothing is done.

Therefore, in this embodiment, the first throat 32 has a resistiveelement 34 having a multiple number of through-holes inserted andengaged into the other end 32 b thereof. Same as the first resistiveelement 33, the resistive element 34 is, for example, a punching metal,ceramic sintered metal or sintered metallic mesh.

Constructed as described above, a phase difference occurs for each ofpressure fluctuations (“−”and “+” in the drawing) between the firstinternal space 31 and the space inside the first throat 32. Therefore,by utilizing this, fluid particles vibrate effectively in theneighborhood of the resistive element 34. As a result, althoughvibration of fluid particles in the neighborhood of the first resistiveelement 33 is insufficient, combustion vibration in a low-frequency areacan be reduced sufficiently.

Additionally, when the resistive element 34 is placed in either positionof one end 32 b having a smaller cross-sectional area than the other end32 a in the first throat 32, same effects can be obtained.

Next, a fourth embodiment of the present invention will be described byreferring to FIG. 4. Characteristic of a fourth embodiment is that sameas the third embodiment, consideration is given to adverse effectsoccurring in the second embodiment.

Namely, in accordance with the relevant embodiment, one end 32 b of thefirst throat 32 protrudes into the first internal space 31, and amultiple number of through-holes 35 are formed in this protrudingportion. Constructed in this manner, because fluid particles vibrateeffectively in each of through-holes 35 by same action as the resistiveelement 34 in the third embodiment, combustion vibration in alow-frequency area can be thoroughly reduced in the same manner as thethird embodiment.

Next, a fifth embodiment of the present invention will be described byreferring to FIG. 5. Characteristic of a fifth embodiment is thatcombustion vibration in a low-frequency area is reduced more thoroughlyas a whole, and a plurality of first box bodies 30 and the like, servingas major components of the first through fourth embodiments, areinstalled in parallel.

By this, an area where the first resistive element 33 exists can beexpanded as a whole. As a result, a ratio of trapping of fluid particlesin a low-frequency area is increased, thereby making it possible toreduce combustion vibration in a low-frequency area more sufficiently asa whole.

Here, in FIG. 5, a plurality of first box bodies 30 and the like (SeeFIG. 4) in accordance with the fourth embodiment are installed inparallel. At least one of the opening area or the length of each of theends 32 b of a first throat 32 and the capacity of each of firstinternal spaces 31 being formed by each of first box bodies 30, ismutually different. By this, vibration properties responding to each offirst box bodies 30 and the like differ, so that it is possible torespond to various combustion vibrations in different frequency areaswithout fail.

Next, a sixth embodiment of the present invention will be described byreferring to FIG. 6. Characteristic of a sixth embodiment is thatfurther consideration is given to combustion vibration in ahigh-frequency area in the fifth embodiment. In a case of combustionvibration in a high-frequency area, wavelength is short. Therefore, aphase difference of pressure fluctuation occurs in the first internalspace 31 itself and consequently, fluid particles do not vibratesufficiently in the neighborhood of the first resistive element 33 orthe resistive element 34 and combustion vibration in a high-frequencyarea cannot be reduced sufficiently if nothing is done.

Therefore, in accordance with the relevant embodiment, a resistiveelement 36 having a multiple number of through-holes is installed to atleast one of each of first internal spaces 31. Same as the firstresistive element 33 and the resistive element 34, the resistive element36 is, for example, a punching metal, ceramic sintered metal or asintered metallic mesh.

Constructed as described above, because fluid particles vibrate in theneighborhood of the resistive element 36 due to a phase difference ofpressure fluctuation being caused by a first internal space 31 itself,combustion vibration in a high-frequency area can be reduced.

Next, a seventh embodiment of the present invention will be described byreferring to FIG. 7. Characteristic of a seventh embodiment is that sameas the sixth embodiment, consideration is given to combustion vibrationin a high-frequency area in the fifth embodiment.

In other words, in accordance with the relevant embodiment, a protrudingplate 37 having a multiple number of through-holes is installed,protruding through each of first internal spaces 31 so as to form aconnecting passageway from an end 32 b of the first throat 32.Constructed as this, because fluid particles effectively vibrate in eachof through-holes of the protruding plate 37 due to same action of theresistive element 36 in accordance with the sixth embodiment, combustionvibration in a high-frequency area can thoroughly be reduced.

Next, an eighth embodiment of the present invention will be described byreferring to FIG. 8. Characteristic of an eighth embodiment is thatcombustion vibration is reduced efficiently. Therefore, an eighthembodiment has an aspect that a plurality of first box bodies 30 and thelike serving as major components of the first through seventhembodiments are installed as if they are installed in a row behind eachother.

To put simply, in accordance with the relevant embodiment, outside thefirst box body 30, is installed in a row a second box body 40 beingsimilar to the first box body 30, and by a cavity inside the second boxbody 40, is formed a second internal space 41 having a predeterminedcapacity. Additionally, the second box body 40 is connected to the firstbox body 30 through a second throat 42 in a tubular form having apredetermined length in a same manner as the first throat 32, and thesecond throat 42 has one end 42 a located on a side of the first boxbody 30 open to a first internal space 31 and has the other end 42 blocated on a side of the second box body 40 open to a second internalspace 41.

Moreover, a second resistive element 43 having a multiple number ofthrough-holes is inserted and engaged into one end 42 a of the secondthroat 42. Same as the first resistive element 33, the second resistiveelement 43 is, for example, a punching metal, ceramic sintered metal ora sintered metallic mesh.

By this, fluid particles not only vibrate in the neighborhood of thefirst resistive element 33 but also resonate with the air in each ofsecond internal spaces 41 being connected through each of second throats42 and vibrate in the neighborhood of each of second resistive elements42, thereby damping the vibration amplitude thereof. As a result, it ispossible to make fluid particles vibrate in a multiple number of placesand consequently, combustion vibration can be reduced efficiently.

Additionally, in FIG. 8, one second box body 40 is installed in a row toso as to be connected to each of first box bodies 30. However, needlessto say, more than two second box bodies 40 may be installed in a row. Inthis case, it is only necessary to connect the second box bodiesadjoining each other through the above-mentioned second throat 42respectively.

Additionally, same as the concept of the second through fifthembodiments of the present invention, the following deformation may bepossible, considering more sufficient response to combustion vibrationin a low-frequency area. Following the first throat 32 in accordancewith the second embodiment, one end 42 a of the second throat 42 has alarger opening area than the other end 42 b. Following the resistiveelement 34 of the first throat 32 in accordance with the thirdembodiment, a resistive element having a multiple number ofthrough-holes is inserted and engaged into the other end 42 b of thesecond throat 42. Following the first throat 32 in accordance with thefourth embodiment, the other end 42 b of the second throat 42 protrudesthrough the second internal space 41 and a multiple number ofthrough-holes are formed in this protruding portion. Following the firstbox bodies 30 and the like in accordance with the fifth embodiment, aplurality of second box bodies 40 and the like are installed in aparallel, and at least one of the opening area or the length of each ofends 42 b of a second throat 42 and the capacity of each of secondinternal spaces 41 is mutually different for every second box body 40.

Furthermore, same as the concept of the sixth and seventh embodiments,the following deformation may be possible, considering more sufficientresponse to combustion vibration in a high-frequency area. Following theresistive element 36 in accordance with the sixth embodiment, at leastone of each of second internal spaces 41 has a resistive element havinga multiple number of through-holes installed. Following the protrudingplate 37 in accordance with the seventh embodiment, at least one ofsecond box bodies 40 has a protruding plate having a multiple number ofthrough-holes installed, protruding through each of second internalspaces 41 and forming a continuous passageway from an end 42 b of thesecond throat 42.

Now, basic concepts of the present invention are explained as above,based on the first through eighth embodiments, and by referring to thedrawings, an example of a gas turbine to which these concepts areapplied concretely will be described. FIG. 9 is a longitudinalcross-sectional view of a necessary portion of a gas turbine to which acombustor in accordance with the above-mentioned first through eighthembodiments are applied concretely, and FIG. 10 is a transversecross-sectional view corresponding to the cross section A-A of FIG. 9.In addition, FIG. 11 shows another example of a gas turbine to which acombustor in accordance with the above-mentioned first through eighthembodiments are applied concretely and is a transverse cross-sectionalview corresponding to the cross-section A-A of FIG. 9. In the drawings,same symbols will be supplied to portions which have same name andfunction as FIG. 1 through FIG. 8 and overlapping explanation will beomitted.

As shown in FIG. 9, a first box body 30 having a fan-shaped side view isinstalled outside and along an elbow portion of the bypass duct 11. Thefirst box body 30, as shown in FIG. 10, has a transverse section thereofconsist of a circular arc portion 30 a and a bending portion 30 b facingtoward a side wall 11 a of the bypass duct 11 from both ends of thecircular arc portion 30 a, and a first internal space 31 is formed bythese circular arc portion 30 a, bending portion 30 b and side wall 11a.

Additionally, three first throats 32 protruding from the side wall 11 aare installed at regular intervals for same degrees in the firstinternal space 31. Each of ends 32 a of these first throats 32 opens tothe internal of the bypass duct 11 from the side wall 11 a while each ofthe other ends 32 b opens to the first internal space 31. Further, eachof ends 32 a of each of first throats 32 has a first resistive element33 having a multiple number of through-holes inserted and engaged.

In other words, construction shown in FIG. 9 and FIG. 10 adopts a bypassduct 11 as an object body 20 and follows the above-mentioned firstembodiment. Additionally, construction shown in FIG. 11 adopts a bypassduct 11 as an object body 20 and follows the above-mentioned fifthembodiment.

The reasons why a bypass duct 11 is adopted as an object body 20 hereare that in order to reduce combustion vibration effectively, a certainsize is necessary for a first internal space 31 and a certain length isnecessary for a first throat 32 and that an area in the neighborhood ofthe bypass duct 11 having a rather sufficient room is suitable. Inconsequence, there are advantages that it is easy to install a first boxbody 30, being installed in order to form a first internal space 31, anda first throat 32, and that it is possible to sufficiently secure afirst internal space 31 having a certain size necessary for effectivereduction of combustion vibration as well as a first throat 32 having acertain length.

Additionally, in accordance with the above-mentioned first througheighth embodiments, shape of transverse cross sections of the firstthroat 32 and the second throat 42 is not only round but also it may bepolygonal.

Next, a ninth through fourteenth embodiments of the present inventionwill be described by referring to the drawings in sequence. FIG. 12 isan exemplary longitudinal cross-sectional view of a necessary portionshowing the neighborhood of a gas turbine combustor in accordance with aninth embodiment of the present invention. In the drawings, same symbolswill be supplied to portions which have same name and function as inFIG. 47 and the overlapping explanations will be omitted. The same willapply to a tenth through fourteenth embodiments of the present inventionto be hereinafter described.

A combustor 3 in accordance with a ninth embodiment of the presentinvention basically has a same construction as what is applied to a gasturbine 1 shown in FIG. 47, but is different in the following points. Toput simply, as shown in FIG. 12, a box body 150 is installed outside therear-end wall of the outer shell 8, and an internal space having apredetermined capacity is formed by a cavity inside the box body 150.Additionally, the box body 150 is connected to the rear-end wall of theouter shell 8 through a tubular throat 151 having a predeterminedlength, and the throat 151 has one end 151 a open to the internal of theouter shell 8, namely to an area upstream of a combustion region, andhas the other end 151 b open to an internal space of the box body 150.

Furthermore, one end 151 a of the throat 151 has a resistive 152 havinga multiple number of through-holes inserted and engaged. The resistiveelement 152 is, for example, a punching metal, ceramic sintered metal ora sintered metallic mesh.

Constructed as described above, the box body 150 functions as anair-container body which accommodates the air for resonance for fluidparticles serving as vibration elements of combustion vibration thatoccurs in a combustion region inside the combustor basket 6.Additionally, the throat 151 functions as a junction body which connectsthe outer shell 8 and the box body 150. Moreover, the resistive element152 functions as a transverse body which crosses the internal of thethroat 151, and through-holes thereof function as vents where fluidparticles are vibrated by resonance with the air inside the box body150. In this way, as for combustion vibration occurring in a combustionregion inside the combustor basket 6, fluid particles serving asvibration elements thereof are propagated to the internal of the outershell 8 through the combustor basket 6; trapped effectively by theresistive element 152; then resonate with the air in an internal spaceof the box body 150; and vibrate in the neighborhood of the resistiveelement 152. By this vibration, vibration amplitude of the fluidparticles is damped and the combustion vibration thereof is reduced. Asa result, a stable decrease in NOx is realized.

An outline arrow in the drawing shows a flow of compressed air that iscompressed by the compressor 2. Compressed air first flows into theinternal of the casing 5; next reverses for approximately 180 degreesafter passing through a tubular space being formed by an outercircumference surface of the combustor basket 6 and an innercircumference surface of the outer shell 8, so as to be introduced intothe internal of the combustor basket 6 from the rear-end side thereof;and then is subject to diffusion combustion and pre-mixed combustionwith a fuel inside the combustor basket 6. Combustion gas produced as aresult is discharged to the turbine 4 from the front end thereof throughthe transition piece 7.

Next, a tenth embodiment of the present invention will be described byreferring to FIG. 13. Characteristic of a tenth embodiment is thatconstruction of the box body 150 in accordance with the ninth embodimentis simplified. This will make an internal space of the box body 150 bein a condition of far higher pressure than the atmosphere pressure.However, as shown in FIG. 12, when the box body 150 itself is installedoutside the combustor 3, namely below the atmosphere pressure,remarkable pressure difference will be caused between the inside and theoutside of the box body 150, so that pressure-tight constructionwithstanding the pressure difference is indispensable for the box body150. As a result, there is a potential that the box body 150 might bemade larger than necessary.

Therefore, in accordance with this embodiment, the box body 150 isinstalled inside the casing 5. Additionally, in installation, it is onlynecessary to bend the throat 151 so as to be inserted into the casing 5.By this, the box body 150 itself is placed inside the casing 5 which isunder approximately same pressure as the internal space, so thatpressure difference between the inside and the outside is scarcelyproduced. As a result, special pressure-tight construction is notnecessary for the box body 150, and the box body 150 does not need toget larger than necessary.

Next, an eleventh embodiment of the present invention will be describedby referring to FIG. 14. Characteristic of an eleventh embodiment isthat an object to which an end 151 a of a throat 151 in accordance withthe ninth and tenth embodiments opens is changed.

To put simply, as shown in FIG. 14, one end 151 a of the throat 151opens to the internal of the combustor basket 6 from a portion of anarea upstream of a combustion region in a side wall of the combustorbasket 6. Additionally, in FIG. 14, the tenth embodiment (See FIG. 13.)is followed, and a change is made to what has the box body 150 installedinside the casing 5. However, needless to say, a change may be made, byfollowing the ninth embodiment (See FIG. 12.). In such a case, thethroat 151 is only necessary to be inserted through the rear-end wall orthe side wall of the outer shell 8 and connected to the side wall of thecombustor basket 6.

Constructed as described above, same as the above-mentioned ninth andtenth embodiments, fluid particles resonate with the air in an internalspace of the box body 150 and vibrate in the neighborhood of a resistiveelement 152, damping the vibration amplitude thereof.

Additionally, an object to which one end 151 a of the throat 151 opensmay be a side wall of the outer shell 8.

Next, a twelfth embodiment of the present invention will be described byreferring to FIG. 15 and FIG. 16. Characteristic of a twelfth embodimentis that combustion vibration is reduced, considering practicality of agas turbine as a whole.

Before describing characteristic of the relevant embodiment, generallayout of a combustor in a gas turbine will be described. As shown inFIG. 15 and FIG. 16, a gas turbine 1 has a plurality of combustors 3installed thereto mainly for a purpose of supplying rotation force to aturbine 4 efficiently. To be concrete, each combustor 3 is installed atregular intervals for same degrees on a same circumference against amain shaft J which directly connects an air compressor 2 and a turbine4. (6 combustors at 60-degree intervals in FIG. 16)

Characteristic of the relevant embodiment will be described hereinafter.A first annulus pipe body 130 having an annulus internal spaceconcentrically with the main shaft J is installed so as to be locatedoutside a rear-end wall of each of outer shells 8. Additionally, thefirst annulus pipe body 130 is connected to the rear-end wall of each ofouter shells 8 respectively through a first throat 131 in a tube formhaving a predetermined length, and the first throat 131 has each of ends131 a open to the internal of each of outer shells 8, namely an areaupstream of a combustion area and has each of the other ends 131 b opento the internal of the first annulus pipe body 130.

Furthermore, one end 131 a of the first throat 131 has a first resistiveelement 132 having a multiple number of through-holes inserted andengaged. Same as the resistive element 152 in accordance with the ninththrough eleventh embodiments, the first resistive element 132 is, forexample, a punching metal, ceramic sintered metal or a sintered metallicmesh.

Constructed as mentioned above, a first annulus pipe body 130 functionsas an air-container body which accommodates the air for resonance forfluid particles serving as vibration elements of combustion vibrationthat occurs in a combustion region inside each of combustor baskets 6.Additionally, each of first throats 131 functions as a junction bodywhich connects each of outer shells 8 and the first annulus pipe body130. Moreover, each of first resistive elements 132 functions as atransverse body which crosses the internal of the first throat 131, andthrough-holes thereof function as vents where fluid particles arevibrated by resonance with the air inside the first annulus pipe body130. In this way, fluid particles serving as vibration elements ofcombustion vibration that occurs in a combustion region inside each ofcombustor baskets 6 are trapped effectively by each of first resistiveelements 132, resonate with the air in the first annulus pipe body 130being connected through each of first throats 131, and vibrate in theneighborhood of each of first resistive elements 132. By this vibration,vibration amplitude of the fluid particles in each of combustors 3 isdamped and the combustion vibration thereof is reduced. As a result, astable decrease in NOx is realized as an entire gas turbine, therebyachieving reduction of NOx in exhaust gas.

Next, a thirteenth embodiment of the present invention will be describedby referring to FIG. 17. Characteristic of a thirteenth embodiment isthat fluid particles are made to vibrate more effectively in theneighborhood of each of first resistive elements 132 in accordance withthe twelfth embodiment. Because an internal space of the first annuluspipe body 130 in accordance with the twelfth embodiment is onecontinuous space, there is a case where a phase difference of pressurefluctuation may occur in the internal space itself. In such a case,fluid particles do not vibrate sufficiently in the neighborhood of eachof first resistive elements 132 and as a result, combustion vibrationcannot be reduced sufficiently if nothing is done.

Consequently, as shown in FIG. 17, in accordance with the relevantembodiment, first dividing wall 135 is installed respectively betweeneach of ends 131 b of each of first throats 131 in the first annuluspipe body 130.

Constructed as described above, an internal space in the first annuluspipe body 130 being one continuous space is divided by a first dividingwall 135 for every first throat 131, namely for every combustor 3,thereby restraining a phase difference of pressure fluctuation fromoccurring in an individual partitioned space. As a result, because fluidparticles vibrate effectively enough in the neighborhood of each offirst resistive elements 132, combustion vibration can be reducedthoroughly.

Next, a fourteenth embodiment of the present invention will be describedby referring to FIG. 18. Characteristic of a fourteenth embodiment isthat combustion vibration in accordance with the twelfth and thirteenthembodiments is reduced efficiently.

To put simply, as shown in FIG. 18, in accordance with the relevantembodiment, a second annulus pipe body 140 having an internal space inthe ring form concentrically with a main shaft J is installed in a rowoutside a first annulus pipe body 130 in the same manner as the firstannulus pipe body 130. Additionally, the second annulus pipe body 140 isconnected to the first annulus pipe body 130 respectively through asecond throat 141 in the tube form having a predetermined length andcorresponding to each of first throats 131, and the second throat 141has each of ends 141 a located on the side of the first annulus pipebody 130 open to the internal of the first annulus pipe body 130 and haseach of the other ends 141 b located on the side of the second annuluspipe body 140 open to the internal of the second annulus pipe body 140.

Furthermore, each of ends 141 a of each of second throats 141 has asecond resistive element 142 having a multiple number of through-holesinserted and engaged. Same as the first resistive element 132, thesecond resistive element 142 is, for example, a punching metal, ceramicsintered metal or a sintered metallic mesh.

Constructed as described above, fluid particles not only vibrate in theneighborhood of each of first resistive elements 132 but also resonatewith the air inside the second annulus pipe body 140 connected througheach of second throats 141 and vibrate in the neighborhood of each ofsecond resistive elements 142, damping the vibration amplitude thereof.As a result, it is possible to make fluid particles vibrate in amultiple number of locations, thereby reducing combustion vibrationefficiently.

In FIG. 18, one second annulus pipe body 140 is installed in a row for afirst annulus pipe body 130, but needless to say, more than two may beinstalled in a row. In this case, it is sufficient only to connectadjoining second annulus pipe bodies 140 through the above-mentionedsecond throat 141 respectively.

Additionally, from a same purpose as the thirteenth embodiment, seconddividing walls (not illustrated) may be installed respectively betweeneach of ends 141 b of each of second throats 141 in the second annuluspipe body 140. By doing this, an internal space of the second annuluspipe body 140 being one continuous space is divided by second dividingwalls for every second throat 141, namely for every combustor 3 througha first throat 131, thereby restraining a phase difference of pressurefluctuation from occurring in an individual space segment. As a result,because fluid particles vibrate effectively enough in the neighborhoodof each of second resistive elements 142, coupled with vibration offluid particles in the neighborhood of each of first resistive elements132, combustion vibration can be reduced more thoroughly.

Moreover, an object to which one end 131 a of each of first throats 131opens may be a side wall of the combustor basket 6 or a side wall of theouter shell 8 as long as it is a part of an area upstream of acombustion region.

Additionally, in accordance with the above-mentioned ninth throughfourteenth embodiments, shape of a transverse cross-section of a throat151 or a first throat 131 or a second throat 141 is not limited to acircle but it may be a polygon.

Next, a fifteenth embodiment through twenty-first embodiments of thepresent invention will be described in sequence by referring to thedrawings. FIG. 19 is a longitudinal cross-sectional view of a combustorin accordance with a fifteenth embodiment of the present invention, andFIG. 20 is a transverse cross-sectional view of a necessary portion ofthe combustor. Additionally, in the drawings, same symbols will besupplied to portions which have same name and same function as in FIG.47 and the overlapping explanations will be omitted. The same will applyto a sixteenth through twenty-first embodiments of the present inventionto be hereinafter described.

A combustor 3 in accordance with a fifteenth embodiment is applied to agas turbine shown in FIG. 47. As shown in FIG. 19 and FIG. 20, thetransition piece 7 is connected to the front end of the combustor basket6 (not illustrated) having a combustion region, and a cylinder body isconstructed by the combustor basket 6 and the transition piece 7 in anarea downstream thereof. The bypass duct 11 is connected to a side wallof the transition piece 7, and one end 11 a thereof opens to theinternal of the transition piece 7 and the other end 11 b opens to theinternal of the casing 5 forming the periphery of the cylinder body.

Furthermore, the bypass duct 11 has a plate-type member 250 installed soas to transverse therein, and the plate-type member 250 has a multiplenumber of through-holes 251 formed therein. Such a plate-type member 250as this is not limited to a metal plate having through-holes 251 drilledthrough but a punching metal, ceramic sintered metal or a sinteredmetallic mesh may be applicable.

Constructed as described above, the casing 5 functions as anair-container body which accommodates the air for resonance for fluidparticles serving as vibration elements of combustion vibration thatoccurs in a combustion region inside the combustor basket 6.Additionally, the bypass duct 11 functions as a junction body whichconnects the transition piece 7 and the casing 5. Moreover, theplate-type member 250 functions as a transverse body which crosses theinternal of the bypass duct 11, and through-holes 251 thereof functionas vents where fluid particles are vibrated by resonance with the airinside the casing 5. In this way, fluid particles serving as vibrationelements of combustion vibration that occurs in a combustion regioninside the combustor basket 6 are propagated through the transitionpiece 7; next introduced from one end 11 a of the bypass duct 11 andtrapped effectively by each of through-holes 251 of the plate-typemember 250; then resonate with the air in the casing 5 being connectedthrough the bypass duct 11 and vibrate through each of through-holes251. By this vibration, vibration amplitude of the fluid particles isdamped and the combustion vibration thereof is reduced. As a result, astable decrease in NOx is realized.

Additionally, in FIG. 19, one plate-type member 250 is installed for thebypass duct 11, but, needless to say, more than two may be installed ina row.

Next, a sixteenth embodiment of the present invention will be describedby referring to FIG. 21 through FIGS. 25A and 25B. Characteristics of asixteenth embodiment are:

-   -   first, combustion vibration is reduced without impairing the        original function of the bypass duct 11; and    -   secondly, easy response is possible to various combustion        vibrations in different frequency areas.

First characteristic requires the bypass duct 11 to originally have afunction to introduce the bypass air from the casing 5 to the internalof the cylinder body (transition piece 7) and adjust the density ofcombustion gas, namely a function to adjust the flow of the bypass air.This is because, while remaining to be so constructed as the fifteenthembodiment, the plate-type member 250 serves as an obstacle, which makesthe bypass air flow insufficient, resulting in such a case as theoriginal function of the bypass duct 11 cannot be carried out.

Second characteristic is for a case where damping responsiveness isdeteriorated remarkably according to frequency areas of combustionvibration because in a region of the plate-type member 250 correspondingto a transverse cross-section of the bypass duct 11, responsiveness ofdamping to various frequency areas of combustion vibration is determinedby the ratio occupying the opening area (sometimes referred as “openingratio” hereinafter) of through-holes 251.

Therefore, in accordance with the relevant embodiment, as shown in FIG.21, the plate-type member 250 is movable by sliding in a transversedirection (an arrow X in the drawing) against the bypass duct 11. Asshown in FIG. 22, the plate-type member 250, being approximately of asame size as a transverse cross-section 11 c of the bypass duct 11, hasthrough-hole areas A1, A2 . . . formed where the ratio occupying theopening area of the through-holes 250 is mutually different, andfurther, has a through-area B, being of an approximately same size asthe transverse cross-section 11 c and penetrating, formed therein.Additionally, in FIG. 21, the opening ratio of the through-holes area A2is larger than that of through-holes area A1.

Moreover, the bypass duct 11 has the bypass valve 12 installed adjacentto the plate-type member 250. Same as the plate-type member 250, thebypass valve 12 is movable by sliding in a transverse direction (anarrow Y in FIG. 21) against the bypass duct 11. To be concrete, becausea plurality of combustors 3 are installed at regular intervals fordegrees on a same circumference against a main shaft of a gas turbine 1,the bypass valve 12, as shown in FIG. 23, has a ring-type plate beingconcentric with the main shaft of the gas turbine 1 serve as afoundation plate portion 12 a, and the foundation plate portion 12 a isinstalled so as to cross the bypass duct 11 of each of combustors 3. Thefoundation plate portion 12 a has through-holes 12 b corresponding toeach of bypass ducts 11 respectively formed therein, and on theperiphery of the foundation plate portion 12 a is fixed a lever 12 cwhich protrudes in a radial direction and is connected to a bypass-valvevariable mechanism 13 (See FIG. 47.).

Then, by operating the bypass-valve variable mechanism 13, the lever 12c moves in a circumferential direction, and with this, the foundationplate member 12 a slides and rotates in a circumferential direction,namely slides to move in a transverse direction (an arrow Y in FIG. 21)against each of bypass ducts 11.

Behavior of the combustor 3 being constructed as mentioned above will bedescribed hereinafter by referring to FIGS. 24A and 24B and FIGS. 25Aand 25B. First, in order to adjust the flow of bypass air, which is theoriginal function of the bypass duct 11, as shown in FIGS. 24A and 24B,the plate-type member 250 is slid to move and selected so as to have thethrough-area B coincide with an area corresponding to a transversecross-section of the bypass duct 11. By sliding the bypass valve 12 tomove in this condition, the degree of opening and closure of the bypassvalve 12 is adjusted, thereby adjusting the flow of the bypass air,which is the original function of the bypass duct 11.

For example, when the bypass air is stopped to flow in by closing thebypass duct 11, the plate-type member 250 is slid to move and selectedso as to have the through-area B coincide with an area corresponding toa transverse cross-section of the bypass duct 11, and at the same time,the bypass valve 12 is slid so as not to cover the through-hole 12 b.(See FIG. 24A.) Also, when the bypass duct 11 is completely opened tohave the bypass air flow in fully, the bypass valve 12 is slid to moveso as to have the through-hole 12 b coincide with an area correspondingto the transverse cross-section of the bypass duct 11. (See FIG. 24B.)Additionally, when the bypass air is adjusted to flow in intermediately,it is only to adjust the ratio of opening so as to have a through-hole12 b partially cover an area corresponding to the transversecross-section of the bypass duct.

When the combustion vibration is to be reduced, as shown in FIGS. 25Aand 25B, the bypass valve 12 is slid to move and selected so as to havethe through-hole 12 b coincide with an area corresponding to thetransverse cross-section of the bypass duct 11. To say simply, thebypass duct 11 is placed in a completely open position. By sliding theplate-type member 250 in this condition, selection is made so thatthrough-holes areas A1, A2 . . . being worth various frequency areas ofcombustion vibration, coincide with an area corresponding to thetransverse cross-section of the bypass duct 11. For example, FIG. 25Ashows a condition where a through-holes area A1 is selected, and FIG.25B is a condition where a through-holes area A2 is selected. By this,responsiveness of damping for combustion vibration of the frequency areathereof is secured, thereby reducing combustion vibration.

As a result, it is possible to surely reduce combustion vibration forvarious frequency areas without damaging the original function of thebypass duct.

Next, a seventeenth embodiment of the present invention will bedescribed by referring to FIG. 26 and FIG. 27. Characteristics of aseventeenth embodiment are that same as the sixteenth embodiment,combustion vibration is reduced without damaging the original functionof the bypass duct 11 and that at the same time, various combustionvibrations in different frequency areas can easily be responded andfurthermore, that construction is simplified.

To put simply, as shown in FIG. 26 and FIG. 27, in accordance with therelevant embodiment, the bypass valve 12 in accordance with thesixteenth embodiment is eliminated, and as a substitute, a plate-typemember 250 have a non-through-holes area C formed, which isapproximately as large as a transverse cross-section 11 c of the bypassduct 11 and has no through-holes 251, in addition to through-holes areaA1, A2 . . . and a through-area B.

Being constructed as mentioned above, when the flow of the bypass air isadjusted, the plate-type member 250 is slid to move appropriately andselected so as to have the through-holes areas A1, A2 . . . ,through-area B and non-through-holes area C coincide with an areacorresponding to the transverse cross-section of the bypass duct 11. Bythis, the degree of opening and closure of the bypass valve 12 isadjusted, thereby adjusting the flow of the bypass air, which is theoriginal function of the bypass duct 11.

On the other hand, when combustion vibration is to be reduced, theplate-type member 250 is slid to move and selected so as to havethrough-holes areas A1, A2 . . . , being worth various frequency areasof combustion vibration, coincide with an area corresponding to thetransverse cross-section of the bypass duct 11. By this, responsivenessof damping to combustion vibration in the frequency-area thereof issecured, thereby reducing the combustion vibration.

As a result, same as the sixth embodiment, combustion vibration invarious frequency areas can surely be reduced without damaging theoriginal function of the bypass duct, and additionally, it is notnecessary to install such the bypass valve 12 as in accordance with thesixteenth embodiment separately. In other words, because the function ofthe bypass valve 12 is shared by the plate-type member 250, there is anadvantage that construction is simple.

Next, an eighteenth embodiment of the present invention will bedescribed by referring to FIG. 28. Characteristic of an eighteenthembodiment is that in the combustor 3 in accordance with the fifteenththrough seventeenth embodiments, the degree of reduction of combustionvibrations can be adjusted. This is because the degree of reduction ofcombustion vibration fluctuates in a distance L from an opening end tothe casing 5 of the bypass duct 11 (the end 11 b in FIG. 19, FIG. 21 andFIG. 26) to the plate-type member 250.

Therefore, in accordance with the relevant embodiment, into the end 11 bof the bypass duct 11 is inserted and engaged a cylindrical member 255being able to protrude axially and having a predetermined length. Bythis, the cylindrical member 255 is made to protrude, which makes thedistance L substantially extend from the plate-type member 250 to thetip of the cylindrical member 255. Therefore, because the distance L canbe adjusted freely by adjustment of protruding amount of the cylindricalmember 255, it is possible to adjust the degree of a decrease incombustion vibration which fluctuates, depending on the distance L. As aresult, setting is possible so as to reduce combustion vibrationthoroughly.

Next, a nineteenth embodiment of the present invention will be describedby referring to FIG. 29. Characteristic of a nineteenth embodiment isthat while in the combustor 3 in accordance with the fifteenth througheighteenth embodiments, the air for resonance inducing vibration offluid particles serves as the air inside the casing 5, in accordancewith the relevant embodiment, the air inside the bypass duct 11 servesas such.

To put simply, in accordance with the relevant embodiment, as shown inFIG. 29, one end 11 a of the bypass duct 11 has a dividing wall 260installed in the neighborhood thereof so as to cross therein, and thedividing wall 260 has a protruding pipe 261 which penetrates through thedividing wall 260 and protrudes through at least one surface thereof.Furthermore, inside the protruding pipe 261, a resistive element 262having a multiple number of through-holes is inserted and engaged. Forthe resistive element 262, for example, a punching metal, ceramicsintered metal or a sintered metallic mesh is applied.

Constructed as described above, the bypass duct 11 functions as anair-container body which accommodates the air for resonance for fluidparticles serving as vibration elements of combustion vibration thatoccurs in a combustion region inside the combustor basket 6.Additionally, a dividing wall 260 and a protruding pipe 261 function asjunction bodies which connect the transition piece 7 and the bypass duct11. Moreover, a resistive element 262 functions as a transverse bodywhich crosses the internal of the protruding pipe 261, and through-holesthereof function as vents where fluid particles are vibrated byresonance with the air inside the bypass duct 11. In this way, as forcombustion vibration that occurs in a combustion region inside thecombustor basket 6, fluid particles are propagated through thetransition piece 7, next introduced from one end 11 a of the bypass duct11 and trapped effectively by the resistive element 262 in theprotruding pipe 261, then resonate with the air in a space from thedividing wall 260 to the other end 11 b in the bypass duct 11 beingconnected through the protruding pipe 261, and vibrate in theneighborhood of the resistive element 262. By this vibration, vibrationamplitude of the fluid particles is damped and the combustion vibrationthereof is reduced. As a result, a stable decrease in NOx is realized.

Additionally, in FIG. 29, one protruding pipe 261 and one resistiveelement 262 are installed for a dividing wall 260, but needless to say,more than two may be installed in a row.

Next, a twentieth embodiment of the present invention will be describedby referring to FIG. 30. Characteristic of a twentieth embodiment isthat combustion vibration is reduced efficiently in the combustor 3 inaccordance with the nineteenth embodiment.

To put simply, in accordance with the relevant embodiment, as shown inFIG. 30, the plurality of dividing walls 260 are installed in a row, andeach of these dividing walls 260 is provided with the protruding pipe261 and the resistive element 262. By this, fluid particles resonatewith the air in each of spaces between the dividing walls 260 beingconnected through each of protruding pipes 261 and vibrate in theneighborhood of each of resistive elements 262, damping the vibrationamplitude thereof. Therefore, it is possible to vibrate fluid particlesin a multiple number of locations, thereby reducing combustion vibrationefficiently.

Next, a twenty-first embodiment of the present invention will bedescribed. Characteristic of a twenty-first embodiment is thatcombustion vibration is reduced sufficiently in the combustor 3 inaccordance with the fifteenth through twentieth embodiments. FIG. 31shows an example of construction thereof.

As shown in FIG. 31, in addition to the plate-type member 250 followingthe fifteenth through eighteenth embodiments, the bypass duct 11 has abox body 230 installed outside a side wall thereof, and a cavity insidethe box body 230 forms an internal space 231 having a predeterminedcapacity. Additionally, the box body 230 is connected to a side wall ofthe bypass duct 11 through a tubular throat 232 having a predeterminedlength, and the throat 232 opens to the internal of the bypass duct 11as well as to an internal space 231.

Furthermore, the throat 232 has a resistive element 233 having amultiple number of through-holes inserted and engaged therein. Same asthe resistive element 262 in accordance with the nineteenth andtwentieth embodiments, the resistive element 233 is, for example, apunching metal, ceramic sintered metal or a sintered metallic mesh.

Constructed as described above, as for combustion vibration that occursin a combustion region inside the combustor basket 6, fluid particlesvibrate not only in through-holes 251 of a plate-type member 250 butalso resonate with the air in an internal space 231 being connectedthrough a throat 232 and vibrate in the neighborhood of a resistiveelement 233 in the throat 232, thereby damping the vibration amplitudethereof. As a result, combustion vibration can be reduced moresufficiently.

In addition, in FIG. 31, construction following the fifteenth througheighteenth embodiments serves as a basis, and the box body 230 and thelike which are characteristic components of the relevant embodiment areadded thereto. However, needless to say, addition may be made to aconstruction following a nineteenth and twentieth embodiments. Also, anobject which is connected through a throat 232 is not limited to a wallsurface of the bypass duct 11 but may be a wall surface of the combustorbasket 6 or the transition piece 7.

Subsequently, a twenty-second through thirty-first embodiments of thepresent invention will be described sequentially by referring to thedrawings. FIG. 32 is a longitudinal cross-sectional view of a necessaryportion of a combustor in accordance with a twenty-second embodiment ofthe present invention, and FIG. 33 is a projected cross-sectional viewof a resonator and a first box body of the combustor that are cutcircumferentially and developed. Additionally, in the drawings, samesymbols will be supplied to portions which have same name and samefunction as in FIG. 47 and the overlapping explanations will be omitted.The same will apply to a twenty-third through thirty-first embodimentsof the present invention to be hereinafter described.

A combustor 3 in accordance with a twenty-second embodiment is appliedto a gas turbine shown in FIG. 47. As shown in FIG. 32, a cylinder bodyis constructed by having the transition piece 7 connected to the frontend of the combustor basket 6 and has a combustion region F wherecombustion vibration is generated with combustion gas inside thecylinder body. The bypass duct 11 is connected to the side wall of thetransition piece 7, and one end thereof opens to the internal of thetransition piece 7 and the other end opens to the casing 5 (notillustrated) forming a periphery of the cylinder body.

Around the outer circumference of the side wall in the neighborhood ofthe combustion region F in the transition piece 7 is installed aresonator 320 (sometimes referred as “acoustic liner” hereinafter), anda cavity 321 is formed by a side wall, front-end wall and rear-end wallof the acoustic liner 320 and a side wall of the transition piece 7.Moreover, on a side wall of the transition piece 7 are formed aplurality of sound-absorption holes 322 penetrating from the internalthereof through the cavity 321, so as to be arranged regularly.

In addition, as shown in FIG. 32 and FIG. 33, outside of the front-endwall of the acoustic liner 320 is installed a first box body 330 so asto be located adjacent, along a side wall of the transition piece 7. Afirst internal space 331 having a predetermined capacity is formed bythe side wall and the front-end wall of the first box body 330, thefront-end wall of the acoustic liner 320 and the side wall of thetransition piece 7. Additionally, the front-end wall of the acousticliner 320 has a first throat 332 having a predetermined length installedso as to protrude toward the first internal space 331, and the firstthroat 332 has one end 332 a open to a cavity 321 of the acoustic liner320 and has the other end 332 b open to the first internal space 331.

Constructed as described above, the first box body 330 functions as anair-container body which accommodates the air for resonance for fluidparticles serving as vibration elements in a low-frequency area ofcombustion vibration that occurs in a combustion region inside thecombustor basket 6. Additionally, the acoustic liner 320 and the firstthroat 332 function as junction boxes which connect a transition piece 7and the first box body 330. Moreover, a side wall of the transitionpiece 7 functions as a transverse body which crosses the internal of theacoustic liner 320, and further, through-holes 322 thereof function asvents where fluid particles in a low-frequency area are vibrated byresonating with the air inside the first box body 330. In this way, asfor combustion vibration that occurs in a combustion region F, fluidparticles serving as vibration elements in a high-frequency area ofcombustion vibration resonate with the air in a cavity 321 inside theacoustic liner 320 and vibrate through the sound-absorption holes 322,thereby damping the vibration amplitude thereof.

On the other hand, fluid particles serving as vibration elements in alow-frequency area resonate with the air inside the first internal space331 through the cavity 321 and the first throat 332 and vibrate throughthe sound-absorption holes 322, thereby damping the vibration amplitudethereof. In this way, combustion vibration is reduced, regardless offrequency areas, and as a result, a stable decrease in NOx is realized.

Additionally, in FIG. 32 and FIG. 33, one first throat 332 is installedfor the first box body 330, but needless to say, more than two may beinstalled.

Next, a twenty-third embodiment of the present invention will bedescribed by referring to FIG. 34 and FIG. 35. Characteristic of atwenty-third embodiment is that adverse effect on combustion vibrationespecially in a high-frequency area is avoided in the twenty-secondembodiment. This is because in addition to expected resonance with theair in a cavity 321 inside an acoustic liner 320, fluid particles in ahigh-frequency area sometimes resonate with the air in a first internalspace 331 through a first throat 332, and in such a case, vibration offluid particles in sound-absorption holes 322 becomes insufficient,degrading an effect to reduce combustion vibration in a high-frequencyarea.

Therefore, according to the relevant embodiment, as shown in FIG. 34 andFIG. 35, the first throat 332 has a first resistive element 333 having amultiple number of through-holes inserted and engaged to one end 332 athereof. The first resistive 333 is for example, a punching metal,ceramic sintered metal or sintered metallic mesh.

Constructed as described above, the first resistive element 333 plays arole as a barrier so as to restrain resonance with the air inside thefirst internal space 331. By this, resonance with the air in a cavity321 inside the acoustic liner 320 is secured, and in consequence, fluidparticles effectively vibrate through the sound-absorption holes 322,thereby damping the vibration amplitude thereof. In addition, forcombustion vibration in a low-frequency area, resonance with the air inthe first internal space 331 is secured, and fluid particles areeffectively trapped by the first resistive element 333 serving asresistance, and vibrate in the neighborhood thereof, thereby damping thevibration amplitude thereof.

Next, a twenty-fourth embodiment of the present invention will bedescribed by referring to FIG. 36 and FIG. 37. Characteristic of atwenty-fourth embodiment is that consideration is given especially tocombustion vibration in a low-frequency area in the twenty-thirdembodiment. When combustion vibration occurs in a low-frequency area, itis necessary to make a cross-sectional area in the first throat 332 inaccordance with the twenty-second embodiment smaller. However, if doingso, an area where the first resistive element 333 exists inevitablybecomes smaller, which reduces the ratio of trapping of fluid particles,contributing insufficiently to a decrease in combustion vibration as awhole.

Therefore, in accordance with the relevant embodiment, as shown in FIG.36 and FIG. 37, such a stepped tubular object is applied for the firstthroat 332 as the inner circumference thereof is rapidly spread from oneend 332 b to the other end 332 a in the neighborhood of the center, andan area of an opening of one end 332 a is larger than that of the otherend 332 b. The end 332 a has a first resistive element 333 inserted andengaged.

Because in this way, it is possible to make the cross-sectional area ofthe internal of the first throat 332, namely the other end 332 b,smaller and at the same time it is possible to expand an area where thefirst resistive element 333 exists, the ratio of trapping of fluidparticles in a low-frequency area is increased, thereby contributingsufficiently to reduction of combustion vibration as a whole. As aresult, it is possible to reduce thoroughly combustion vibration in alow-frequency area as a whole.

Additionally, when a trumpet-like object whose inner circumferencegradually expands is applied as the first throat 332, same effects canbe obtained.

Next, a twenty-fifth embodiment of the present invention will bedescribed by referring to FIG. 38 and FIG. 39. Characteristic of atwenty-fifth embodiment is that consideration is given to an adverseeffect caused in accordance with the twenty-fourth embodiment. When theopening area of one end 332 a of the first throat 332 is larger thanthat of the other end 332 b as in accordance with the twenty-fourthembodiment, in other words, when the capacity inside the first throat332 becomes larger, sometimes no phase difference of each of pressurefluctuations occurs between a space inside the first throat 332 beingisolated by the first resistive element 333 and a cavity 321 inside anacoustic liner 320. In such a case, because fluid particles do notvibrate in the neighborhood of the first resistive element 333, such anadverse effect is caused as combustion vibration in a low-frequency arecannot be reduced sufficiently if nothing is done.

Therefore, in accordance with the relevant embodiment, as shown in FIG.38 and FIG. 39, one end 332 b of the first throat 332 has a resistiveelement 334 having a multiple number of through-holes inserted andengaged. Same as the first resistive elements 333, the resistive element334 is, for example, a punching metal, ceramic sintered metal or asintered metallic mesh.

Constructed as described above, because a phase difference of each ofpressure fluctuations occurs between a first internal space 331 and aspace inside the first throat 332, in order to make fluid particlesvibrate effectively in the neighborhood of a resistive element 334, byutilizing this, combustion vibration in a low-frequency area can bereduced sufficiently, although vibration of fluid particles in theneighborhood of the first resistive element 333 is insufficient.

Moreover, same effect can be obtained although the resistive element 334is installed to either side of the end 332 b which has a smallercross-sectional area than the other end 332 a of the first throat 332.

Next, a twenty-sixth embodiment of the present invention will bedescribed by referring to FIG. 40. Characteristic of a twenty-sixthembodiment is that combustion vibration in a low-frequency area isreduced more sufficiently, and a plurality of first box bodies 330 andthe like serving as major components of the twenty-second throughtwenty-fifth embodiments are installed in parallel to the acoustic liner320.

To put simply, as shown in FIG. 40, outside the front-end wall of theacoustic liner 320 are installed two first box bodies 330 beinginstalled in parallel in a circumferential direction along a side wallof the transition piece 7, so as to be located adjacent to each other.Each of first internal spaces 331 being formed by each of first boxbodies 330 open to a cavity 321 of the acoustic liner 320 through thefirst throat 332 being installed respectively.

By this, it is possible to substantially expand the capacity of thefirst internal space 331 as a whole, thereby enhancing efficiency ofresonance with the air in the first internal space 331 for combustionvibration in a low-frequency area. As a result, vibration efficiency offluid particles being caused by this resonance is enhanced, therebymaking it possible to reduce combustion vibration in a low-frequencyarea more sufficiently as a whole.

Here, in FIG. 40, two sets of first box bodies 330 and the like inaccordance with the twenty-second embodiment are installed in parallelfor an acoustic liner 320. Needless to say, more than those may beinstalled in parallel, and a plurality of first box bodies 330 and thelike in accordance with the twenty-third through twenty-fifthembodiments may be installed in parallel. Additionally, each of firstbox bodies 330 has a first wall surface 330 a being shared to be usedfor forming a first internal space 331 thereof respectively and isdirectly adjoining to each other across the first wall surface 330 a,but may be placed adjoining independently.

In addition, when the opening area or the length of each of ends 332 bof the first throat 332, or the capacity of each of first internalspaces 331 being formed by each of first box bodies 330 is determinedappropriately in advance so as to be mutually different, vibrationproperties responding to each of first box bodies 330 and the like willdiffer, so that it is possible to respond to various combustionvibrations in different frequency areas without fail.

Next, a twenty-seventh embodiment of the present invention will bedescribed by referring to FIG. 41. Characteristic of a twenty-seventhembodiment is that a phase difference of pressure fluctuation in acavity 321 inside the acoustic liner 320 in accordance with thetwenty-sixth embodiment is restrained from occurring. In accordance withthe twenty-sixth embodiment, a phase difference of pressure fluctuationoccurs in the cavity 321 itself, and in such a case, vibration of fluidparticles through sound-absorption holes 322 becomes insufficient incombustion vibration in a high-frequency area, and vibration of fluidparticles through sound-absorption holes 322 and vibration of fluidparticles in the neighborhood of the first resistive element 333 or theresistive element 334 become insufficient in combustion vibration in alow-frequency area, which cannot reduce combustion vibrationsufficiently if nothing is done.

Therefore, in accordance with the relevant embodiment, as shown in FIG.41, a dividing wall 323 is installed respectively between each of ends332 a of each of first throats 332 in the cavity 321 of the acousticliner 320.

Constructed as described above, the cavity 321 is divided by thedividing wall 323 for every first throat 332, thereby making it possibleto restrain a phase difference of pressure fluctuation in an individualdivided space from occurring. As a result, in combustion vibration in ahigh-frequency area, fluid particles vibrate effectively throughsound-absorption holes 322, and in combustion vibration in alow-frequency area, fluid particles vibrate through sound-absorptionholes 322 and vibrate in the neighborhood of the first resistive elementand the like effectively, thereby making it possible to reducecombustion vibration thoroughly.

Next, a twenty-eighth embodiment of the present invention will bedescribed by referring to FIG. 42. Characteristic of a twenty-eightembodiment is to effectively utilize a phase difference of pressurefluctuation in a cavity 321 inside an acoustic liner 320 that may occurin the twenty-seventh embodiment while it is restrained in theabove-mentioned twenty-seventh embodiment.

To put simply, as shown in FIG. 42, dividing walls 323 being installedin a cavity 321 inside the acoustic liner 320 in accordance with thetwenty-sixth embodiment has a multiple number of through-holes formedtherein, and these dividing walls 323 play a role as resistive elements.By this, compared with mutual pressure fluctuation, a phase differenceoccurs substantially between adjoining divided spaces inside theacoustic liner 320 being separated by the dividing walls 323. As aresult, fluid particles begin to vibrate effectively throughthrough-holes of the dividing walls 323, thereby making it possible toreduce combustion vibration more sufficiently.

Next, a twenty-ninth embodiment of the present invention will bedescribed by referring to FIG. 43. Characteristic of a twenty-ninthembodiment is that combustion vibration in a low-frequency area isreduced more sufficiently, by effectively utilizing a phase differenceof pressure fluctuation that may occur between first box bodies 330adjoining each other in the twenty-sixth through twenty-eighthembodiment.

To put simply, as shown in FIG. 43, among wall surfaces of each of firstbox bodies 330, a first wall surface 330 a, being shared and used forforming a first internal space 331, has a multiple number ofthrough-holes formed, and this first wall surface 330 a serves as aresistive element. By this, the first internal spaces 331 being isolatedby the first wall surface 330 a and adjoining each other has a phasedifference produced substantially when pressure fluctuations thereof arecompared with each other. As a result, fluid particles effectivelyvibrate through through-holes of the first wall surface 330 a, therebymaking it possible to reduce combustion vibration in a low-frequencyarea more sufficiently.

Next, a thirtieth embodiment of the present invention will be describedby referring to FIG. 44. Characteristic of a thirtieth embodiment isthat in addition to a problem of combustion vibration, the followingproblems specific to a combustor 3 are solved.

First problem is that because of having a combustion region F inside,the combustor basket 6 and the transition piece 7 which serve ascylinder bodies having a resonator 3 installed around the outercircumference thereof are subject to an environment of continuallyheating, which eventually results in heating of the acoustic liner 320and the first box body 330. Therefore, it is required to prevent thesecylinder body, acoustic liner 320 and the like from being subject toexcessive increase in temperature.

Second problem is that sometimes a part of combustion gas beinggenerated in a combustion region F in a cylinder body flows into theinternal of the acoustic liner 320 or internal of the first box body 330by way of sound-absorption holes 322 and further through the firstthroat 332. In such a case, a fuel and water vapor being contained in apart of combustion gas is liquefied and accumulates inadvertently.Therefore, it is required to discharge this inadvertent stagnant liquidoutside the acoustic liner 320 and the first box body 330.

Therefore, as shown in FIG. 44, in accordance with the relevantembodiment, the acoustic liner 320 and the first box body 330 have aplurality of fluid-introducing holes 324 for cooling of the acousticliner and a plurality of fluid-introducing holes 335 for cooling of thefirst box body formed therein, which introduce from outside to insiderespectively the cooling fluid, namely the compressed air flowing intothe internal of the casing 5 from the compressor 2. By this, theacoustic liner 320 and the first box body 330 are directly cooled, andat the same time the combustor basket 6 and the transition piece 7serving as cylinder bodies are indirectly cooled. As a result, itbecomes possible to prevent an excessive increase in temperature beingcaused by combustion, thereby solving the above-mentioned first problem.

Additionally, the vertically lowest portion of the acoustic liner 320and the first box body 330 have a drain hole 325 for the acoustic linerand a drain hole 336 for the first box body, which discharge stagnantliquid from inside to outside respectively. By this, it is possible todischarge outside inadvertent stagnant liquid being accumulated insidethe acoustic liner 320 and the first box body 330, thereby solving theabove-mentioned second problem.

Next, a thirty-first embodiment of the present invention will bedescribed by referring to FIG. 45 and FIG. 46. Characteristic of athirty-first embodiment is that combustion vibration is reduced moreefficiently. Therefore, a first box body 330 and the like serving asmajor components of the above-mentioned twenty-second through thirtiethembodiments are installed in such a manner as if a plurality areinstalled in a row.

To put simply, in accordance with the relative embodiment, as shown inFIG. 45 and FIG. 46, outside a front-end wall of the first box body 330,is installed in a row along a side wall of the transition piece 7 asecond box body 340 being similar to a first box body 330; and a sidewall and the front-end wall of the second box body 340, the front-endwall of the first box body 330 and a side wall of the transition piece 7have a second internal space 341 having a predetermined capacity formed.Furthermore, the front-end wall of the first box body 330 has a secondthroat 342 having a predetermined length installed thereto, protrudingtoward the second internal space 341. The second throat 342 has one end342 a located on a side of the first box body 330 open to the firstinternal space 331 and has the other end 342 b located on a side of thesecond box body 340 open to the second internal space 341.

Additionally, the second throat 342 has a second resistive element 343having a multiple number of through-holes inserted and engaged to an end342 a thereof. Same as the first resistive element 333, the secondresistive element 343 is, for example, a punching metal, a ceramicsintered metal or sintered metallic mesh. Moreover, in FIG. 45 and FIG.46, a second box body 340 and the like are added to construction inaccordance with the twenty-second embodiment (See FIG. 32 and FIG. 33.),but needless to say, may be added to construction in accordance with thetwenty-third through thirtieth embodiments (FIG. 34 through FIG. 44.).

By this, fluid particles in a low-frequency area not only vibratethrough sound-absorption holes 322 or vibrate in the neighborhood of thefirst resistive element 333 and the like but also resonate with the airin the second internal space 341 so as to vibrate in the neighborhood ofthe second resistive element 343, thereby damping the vibrationamplitude thereof. As a result, fluid particles can vibrate in amultiple number of locations, which makes it possible to efficientlyreduce combustion vibration in a low-frequency area.

Additionally, in FIG. 45 and FIG. 46, one second box body 340 isinstalled in a row for the first box body 330, but needless to say, morethan two may be installed in a row. In such a case, it is only todirectly connect the second internal spaces 341 in the adjoining secondbox bodies 340 through the above-mentioned second throat 342respectively.

Moreover, same as concepts of the twenty-fourth through twenty-sixthembodiments, considering sufficient response to combustion vibration ina low-frequency area, the following modifications are possible.Following the first throat 332 in accordance with the twenty-fourthembodiment, an opening area of one end 342 a of the second throat 342 islarger than that of the other end 342 b. Following the resistive element334 of the first throat 332 in accordance with the twenty-fifthembodiment, one end 342 b of the second throat 342 has a resistiveelement having a multiple number of through-holes inserted and engaged.Following the first box body 330 in accordance with the twenty-sixthembodiment, a plurality of second box bodies 340 and the like areinstalled in parallel.

Furthermore, same as a concept of the twenty-ninth embodiment, in orderto utilize a phase difference of pressure fluctuation between adjoiningsecond box bodies 340 being installed in parallel, each of adjoiningsecond box bodies 340 being installed in parallel has a second wallsurface 340 a which is shared so as to form a second internal space 341mutually, and the second wall surface 340 a can have a multiple numberof through-holes as resistive elements.

In addition, same as a concept of the thirtieth embodiment, in order tosolve a problem peculiar to a combustor 3, the second box body 340 has aplurality of fluid-introducing holes for cooling of a second box body,introducing the cooling fluid from outside to inside, formed therein,and furthermore, has a drain hole for the second box body, dischargingstagnant liquid from inside to outside, formed therein.

Moreover, in accordance with the twenty-second through thirty-firstembodiments, a shape of a transverse cross-section of the first throat331 or the second throat 341 is not limited to a circle but may be apolygon. In addition, the first box body 330 or the second box body 340may have the first internal space 331 or the second internal space 341formed by an internal cavity respectively. In such a case, it is only todirectly connect to the acoustic liner 320 or the first box body 330through the first throat 332 or the second throat 342 respectively.

While the invention has been described in connection with what ispresently considered to be the most practical and preferred embodiment,it is to be understood that the invention is not to be limited to thedisclosed embodiments or an example to which these embodiments areapplied concretely, but on the contrary, is intended to cover variousmodifications and equivalent arrangements included within the spirit andscope of the appended claims.

INDUSTRIAL APPLICABILITY

As described above, the present invention is useful for a gas turbinecombustor and a gas turbine for which realization of reduction of NOx isdesired.

1. A gas turbine combustor consisting of a cylinder body which has acombustion region therein, comprising: an air-container body whichaccommodates air for resonance for fluid particles serving as vibrationelements of combustion vibration being generated in the said combustionregion; a junction body having a predetermined length which has one endthereof open to the said cylinder body and has other end thereof open tothe said air-container body; and a transverse body having vents wherethe said fluid particles cross internal of junction body and vibrate byresonance with air in the said air-container body.
 2. A gas turbinecombustor as described in claim 1: wherein, the said air-container bodyconsists of a first box body which is installed outside the saidcylinder body so as to form a first internal space having apredetermined capacity; the said junction body consists of a firstthroat which has one end thereof open to the said combustion region ordownstream area thereof and has other end thereof open to the said firstinternal space; and the said transverse body consists of a firstresistive element which has a multiple number of through-holes as thesaid vents and is inserted and engaged into the said one end of the saidfirst throat.
 3. A gas turbine combustor as described in claim 2:wherein, a bypass duct for adjustment of density of combustion gas isprovided, which not only opens to the said combustion region ordownstream area thereof in the said cylinder body but also opens to aninternal of a casing forming a periphery of the said cylinder body, andsupplies bypass air to an internal of the said cylinder body from thesaid casing; wherein, the said one end of the said first throat open toan internal of bypass duct.
 4. A gas turbine combustor as described inclaim 2: wherein, an opening area of the said one end of the said firstthroat is larger than that of the said other end.
 5. A gas turbinecombustor as described in claim 4: wherein, the said other end of thesaid first throat has a resistive element having a multiple number ofthrough-holes inserted and engaged.
 6. A gas turbine combustor asdescribed in claim 4: wherein, the said other end of the said firstthroat protrudes through the said first internal space and has amultiple number of through-holes formed in protruding portion thereof.7. A gas turbine combustor as described in claim 2: wherein, a pluralitynumber of the said box bodies are installed in parallel.
 8. A gasturbine combustor as described in claim 7: wherein, at least one ofopening area or length of each of the said other ends of the said firstthroat or capacity of each of the said first internal spaces differsfrom each other for every said first box body.
 9. A gas turbinecombustor as described in claim 7: wherein, at least one of each of thesaid first internal spaces has a resistive element having a multiplenumber of through-holes installed.
 10. A gas turbine combustor asdescribed in claim 7: wherein, at least one of each of the said firstbox bodies has a protruding plate installed, which protrudes througheach of the said first internal spaces so as to form a continuouspassageway from the said other end of the said first throat and has amultiple number of through-holes.
 11. A gas turbine combustor asdescribed in claim 2, comprising: a second box body at least one ofwhich is installed, connecting to outside of the said first box body soas to form a second internal space having a predetermined capacity,respectively; and a second throat having a predetermined length whichopens respectively to the said adjoining first and second internalspaces; wherein, each of the said second throats has a second resistiveelement having a multiple number of through-holes inserted and engagedto one end thereof being located on a side of the said first box body.12. A gas turbine combustor as described in claim 11: wherein, anopening area of the said one end of the said second throat is largerthan that of other end thereof.
 13. A gas turbine combustor as describedin claim 12: wherein, the said other end of the said second throat has aresistive element having a multiple number of through-holes inserted andengaged.
 14. A gas turbine combustor as described in claim 12: wherein,the said other end of the said second throat protrudes through the saidsecond internal space and has a multiple number of through-holes formedin protruding portion thereof.
 15. A gas turbine combustor as describedin claim 11: wherein, a plurality of the said second box bodies areinstalled in parallel.
 16. A gas turbine combustor as described in claim15: wherein, at least one of opening area or length of each of the saidother ends of the said second throat or capacity of each of the saidsecond internal spaces differs from each other for every said second boxbody.
 17. A gas turbine combustor as described in claim 15: wherein, atleast one of each of the said second internal spaces has a resistiveelement having a multiple number of through-holes installed.
 18. A gasturbine combustor as described in claim 15: wherein, at least one ofeach of the said second box bodies has a protruding plate installed,which protrudes through each of the said second internal spaces so as toform a continuous passageway starting from the said other end of thesaid second throat and has a multiple number of through-holes.
 19. A gasturbine, comprising an air compressor, a gas turbine combustor asdescribed in claim 2, and a turbine.
 20. A gas turbine combustor asdescribed in claim 1: wherein, the said air-container body consists of abox body which is installed outside the said cylinder body and so as toform an internal space having a predetermined capacity; the saidjunction body consists of a throat which has one end thereof open to anarea upstream of the said combustion region and has other end thereofopen to the said internal space; and the said transverse body consistsof a resistive element which has a multiple number of through-holesserving as the said vents and is inserted and engaged into the said oneend of the said throat.
 21. A gas turbine combustor as described inclaim 20: wherein, the said box body is installed inside a casingforming a periphery of the said cylinder body.
 22. A gas turbine,comprising: an air compressor and a turbine that are directly connectedto each other by a main shaft; and a gas turbine compressor as describedin claim 20 that is installed between the said air compressor and thesaid turbine.
 23. A gas turbine, comprising: an air compressor and aturbine that are directly connected to each other by a main shaft; and aplurality of gas turbine combustors as described in claim 1 that areinstalled on a same circumference of the said main shaft between thesaid air compressor and the said turbine: wherein, the saidair-container body consists of a first annulus pipe body which isinstalled outside a rear-end of each of the said cylinder bodies, beingconcentric with the said main shaft; the said junction body consists ofa first throat which has each of one ends thereof open to an areupstream area of each of the said combustion regions and has each ofother ends thereof open to an internal of the said first annulus pipebody; and the said transverse body consists of a first resistive elementwhich has a multiple number of through-holes serving as the said ventsand is inserted and engaged into each of the said one ends of each ofthe said first throats.
 24. A gas turbine combustor as described inclaim 23: wherein, a first dividing wall is installed, respectively,between each of said other ends of each of the said first throats insidethe said first annulus pipe body.
 25. A gas turbine combustor asdescribed in claim 23, comprising: at least one second annulus pipe bodywhich is installed, connecting to outside of the said first annulus pipebody and being concentric with the said main shaft; and a second throathaving a predetermined length which corresponds to each of the saidfirst throats and opens to internals of the said adjoining first andsecond annulus pipe bodies, respectively; wherein, each of the saidsecond throat has a second resistive element having a multiple number ofthrough-holes inserted and engaged to each of one ends located on a sideof the said first annulus pipe body.
 26. A gas turbine combustor asdescribed in claim 25: wherein, a second dividing wall is installed,respectively, between each of the said other ends of each of the saidsecond throats inside the said second annulus pipe body.
 27. A gasturbine combustor as described in claim 1: wherein, the said junctionbody consists of a bypass duct which has one end open to the saidcombustion region or downstream area thereof in the said cylinder bodyand has other end thereof open to an internal of a casing forming aperiphery of the said cylinder body; the said air-container bodyconsists of the said casing; and the said transverse body consists of aplate-type member having a multiple number of through-holes serving asthe said vents.
 28. A gas turbine combustor as described in claim 27:wherein, the said plate-type member is movable by sliding in atransverse direction against the said bypass duct, being ofapproximately same size as a transverse cross-section of the said bypassduct and having a plurality of through-holes areas in which a ratio ofopening area of the said through-holes is different from each other. 29.A gas turbine combustor as described in claim 28: wherein, the saidbypass duct is provided with a bypass valve which adjusts, by degree ofopening and closure, a flow of bypass air being introduced into aninternal of the said cylinder body from the said casing through the saidbypass duct; and the said plate-type member has a through area to gothrough for an approximately same size as a transverse cross-section ofthe said bypass duct.
 30. A gas turbine combustor as described in claim28: wherein, the said plate-type member has a through-area to go throughfor an approximately same size as a transverse cross-section of the saidbypass duct, and a non-through-holes area not to exist the saidthrough-holes for an approximately same size as a transversecross-section of the said bypass duct.
 31. A gas turbine combustor asdescribed in claim 27: wherein, the said other end of the said bypassduct has a cylindrical member having a predetermined length inserted andengaged, which can protrude therein and out in a direction of an axisthereof.
 32. A gas turbine combustor as described in claim 1: wherein,the said air-container body consists of a bypass duct which has one endthereof open to the said combustion region or downstream area thereof inthe said cylinder body and has other end thereof open to an internal ofa casing forming a periphery of the said cylinder body; the saidjunction body consists of a dividing wall which crosses neighborhood ofthe said one end of the said bypass duct, and a protruding pipe whichpenetrates through the said dividing wall and protrudes through at leastone surface of the said dividing wall; and the said transverse bodyconsists of a resistive element which has a multiple number ofthrough-holes serving as the said vents and is inserted and engaged tothe said protruding pipe.
 33. A gas turbine combustor as described inclaim 32: wherein, a plurality of the said dividing walls are installedin a row; and each of dividing walls is provided with the saidprotruding pipe and the said resistive element.
 34. A gas turbinecombustor as described in claim 27, comprising: a box body which isinstalled outside the said cylinder body so as to form an internal spacehaving a predetermined space; and a throat having a predetermined lengthwhich opens to the said combustion region or downstream area thereof andopens to the said internal space; wherein, the said throat has aresistive element having a multiple number of through-holes inserted andengaged.
 35. A gas turbine, comprising an air compressor, a gas turbinecombustor as described in claim 27, and a turbine.
 36. A gas turbinecombustor as described in claim 1: wherein, the said cylinder body has aresonator having a cavity installed around periphery thereof and hassound-absorption holes opening to the said cavity formed; wherein, thesaid air-container body consists of a first box body which is installedadjacent to the said resonator so as to form a first internal spacehaving a predetermined capacity; the said junction body consists of thesaid resonator and a first throat which has one end thereof open to thesaid cavity and has other end thereof open to the said first internalspace; and the said transverse body consists of a side wall of the saidcylinder body having the said sound-absorption holes serving as the saidvents.
 37. A gas turbine combustor as described in claim 36: wherein,the said first throat has a first resistive element having a multiplenumber of through-holes inserted engaged to the said one end.
 38. A gasturbine combustor as described in claim 37: wherein, an opening area ofthe said one end of the said first throat is larger than that of thesaid other end.
 39. A gas turbine combustor as described in claim 38:wherein, the said first throat has a resistive element having a multiplenumber of through-holes inserted and engaged to the said other end. 40.A gas turbine combustor as described in claim 36: wherein, a pluralityof the said first box bodies are installed in parallel to the saidresonator.
 41. A gas turbine combustor as described in claim 40:wherein, a dividing wall is installed, respectively, between each of thesaid one ends of each of the said first throats in the said cavity ofthe said resonator.
 42. A gas turbine combustor as described in claim41: wherein, the said dividing wall serves as a resistive element havinga multiple number of through-holes.
 43. A gas turbine combustor asdescribed in claim 40: wherein, each of the said first box bodies beinginstalled in parallel and adjoining each other has a first wall surfacewhich is shared so as to form the said internal space, respectively; andthe said first wall surface serves as a resistive element having amultiple number of through-holes.
 44. A gas turbine combustor asdescribed in claim 36: wherein, the said resonator and the said firstbox body have a plurality of fluid-introducing holes formed therein,which introduce cooling fluid from outside to inside, respectively. 45.A gas turbine combustor as described in claim 36: wherein, the saidresonator and the said first box body have a drain hole formed therein,which discharges stagnant liquid from inside to outside, respectively.46. A gas turbine combustor as described in claim 36, comprising: atleast one second box body which is installed, connecting to outside thesaid first box body, so as to form a second internal space having apredetermined capacity, respectively; and a second throat having apredetermined length which opens to the said adjoining first and secondinternal spaces, respectively; wherein, each of the said second throatshas a second resistive element having a multiple number of through-holesinserted and engaged to one end located on side of the said first boxbody.
 47. A gas turbine combustor as described in claim 46: wherein, anopening area of the said one end of the said second throat is largerthan that of other end thereof.
 48. A gas turbine combustor as describedin claim 47: wherein, the said second throat has a resistive elementhaving a multiple number of through-holes inserted and engaged to thesaid other end.
 49. A gas turbine combustor as described in claim 46:wherein, a plurality of the said second box bodies are installed to thesaid first box body in parallel.
 50. A gas turbine combustor asdescribed in claim 49: wherein, each of the said second box bodies beinginstalled in parallel and adjoining has a second wall surface that isshared so as to form the said second internal space, respectively, andserves as a resistive element having a multiple number of through-holesin the said second wall surface thereof.
 51. A gas turbine combustor asdescribed in claim 46: wherein, the said second box body has a pluralityof fluid-introducing holes formed therein, which introduce cooling fluidfrom outside to inside.
 52. A gas turbine combustor as described inclaim 46: wherein, the said second box body has a drain hole formedtherein, which discharges stagnant liquid from inside to outside.
 53. Agas turbine, comprising an air compressor, a gas turbine combustordescribed as claim 36, and a turbine.
 54. A gas turbine combustor asdescribed in claim 32, comprising: a box body which is installed outsidethe said cylinder body so as to form an internal space having apredetermined space; and a throat having a predetermined length whichopens to the said combustion region or downstream area thereof and opensto the said internal space; wherein, the said throat has a resistiveelement having a multiple number of through-holes inserted and engaged.55. A gas turbine, comprising an air compressor, a gas turbine combustoras described in claim 32, and a turbine.